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EP3459845B1 - Giravion avec collecteur d'échappement permettant de combiner un panache d'échappement de système - Google Patents

Giravion avec collecteur d'échappement permettant de combiner un panache d'échappement de système Download PDF

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Publication number
EP3459845B1
EP3459845B1 EP17203232.8A EP17203232A EP3459845B1 EP 3459845 B1 EP3459845 B1 EP 3459845B1 EP 17203232 A EP17203232 A EP 17203232A EP 3459845 B1 EP3459845 B1 EP 3459845B1
Authority
EP
European Patent Office
Prior art keywords
exhaust
rotorcraft
cowl
platform
ducts
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17203232.8A
Other languages
German (de)
English (en)
Other versions
EP3459845A1 (fr
Inventor
Keith C. Pedersen
Brent SCANNELL
Nam Dai TRAN
Thomas Mast
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Priority to EP19189876.6A priority Critical patent/EP3584160B1/fr
Publication of EP3459845A1 publication Critical patent/EP3459845A1/fr
Application granted granted Critical
Publication of EP3459845B1 publication Critical patent/EP3459845B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features
    • F01N13/08—Other arrangements or adaptations of exhaust conduits
    • F01N13/10—Other arrangements or adaptations of exhaust conduits of exhaust manifolds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P1/00—Air cooling
    • F01P1/06—Arrangements for cooling other engine or machine parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
    • F01P11/10—Guiding or ducting cooling-air, to, or from, liquid-to-air heat exchangers

Definitions

  • This disclosure relates generally to an exhaust system for an aircraft and more particularly, though not exclusively, to an exhaust manifold for combining aircraft system exhausts.
  • An aircraft generally includes an exhaust system for expelling hot exhaust gases in a safe and efficient manner.
  • Exhaust gases may reach temperatures of greater than 232,2 degrees Celsius (450 degrees Fahrenheit) and are likely to cause damage or disruption to objects that they may be directed to when expelled.
  • hot air around an aircraft tail boom or aircraft rotors may cause the structures to weaken and may affect performance.
  • exhaust systems are typically designed with plumbing to expel exhaust aft of equipment inlets, particularly the engine inlet, so that the exhaust is not re-ingested into the equipment.
  • EP 0013,272 (A1 ) discloses a rotorcraft with engine inlet and exhaust.
  • GB 638,093 discloses an aircraft gas-turbine-engine power plant of the type comprising an airscrew driven by the gas turbine engine. Exhaust gases are led to passages in the propeller blades to prevent ice formation on the blades. Exhaust from the gas turbine power plant enters a fixed manifold and from thence to a moving manifold and ducts to the muffs surrounding the blade roots. These lead the gases to spaces in the blades. Additional conduits lead the gases through the manifolds to the forward propeller. Plates of part spherical shape close the aperture in the spinners.
  • EP 2,724,934 discloses a hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller.
  • a rotorcraft according to claim 1.
  • Optional features of the rotorcraft are set out in the dependent claims.
  • an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of the equipment inlets and directing the exhausts upwards towards the rotor disc such that the exhaust is expelled and diffused forward of the engine inlets.
  • the exhaust manifold may combine and expel system exhaust, for example, from an electric generator, an oil cooler, an environmental control system, and/or other equipment located upstream from the engine and other equipment inlets.
  • the exhaust manifold may include exhaust ducts, air ducts, flexible hosing, and other plumbing to direct hot exhaust towards the aircraft rotor linkages, such that the exhaust is expelled forward of the engine and other equipment inlets, but not re-ingested into the engine or the other equipment.
  • the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft.
  • the exhaust manifold may include a platform that contains exhaust ducts where the platform is shaped to provide mechanical support to the transmission cowling along the top of the aircraft.
  • the exhaust manifold may include a frame extending from the underside of the platform that follows the contours of the transmission cowling such that, when the transmission cowling is in a closed position, the cowling lays along the support frame for additional mechanical support.
  • An aircraft may include an exhaust manifold for combining multiple system exhausts located upstream of the engine and other equipment inlets, and directing the exhausts upward towards a rotor disc to expel and diffuse the exhausts away from the aircraft.
  • the exhaust manifold may combine and expel system exhaust, for example, from an electric generator and an oil cooler.
  • the exhaust manifold may further combine and expel exhaust from an environmental control system, or other equipment located upstream from the engine and other equipment inlets.
  • the manifold may include air ducts, flexible hosing, or other plumbing to direct hot exhaust towards the aircraft rotor linkages, so that the hot exhaust may dissipate away from the aircraft rotors and away from the engine inlets.
  • the exhaust manifold may include structures for supporting a transmission cowling.
  • the exhaust manifold may include a platform that contains the air ducts where the platform is shaped to fit within the contours of the aircraft. The outside edges of the platform may attach and provide mechanical support to the transmission cowling along the top of the aircraft.
  • the exhaust manifold platform may include a frame or bracket extending from the bottom and/or sides of the platform that may attach to the floor or base of the transmission compartment and may match the contours of the transmission cowling along the sides of the aircraft. When the transmission cowling is in a closed position, the cowling lays along the support frame to provide additional reinforcement.
  • FIGURES 1-4 illustrate an exemplary rotorcraft having a vertical rotor on the top of the aircraft that includes an exhaust manifold for combining system exhausts for equipment located upstream of the engine inlets, and directing the exhaust towards the rotor linkages.
  • FIGURES 1A and 1B illustrate an example embodiment of a rotorcraft 101.
  • FIGURE 1A illustrates a side view of rotorcraft 101
  • FIGURE 1B illustrates a perspective view of rotorcraft 101.
  • Rotorcraft 101 has a rotor system 103 with a plurality of rotor blades 105. The pitch of each rotor blade 105 may be managed or adjusted in order to selectively control direction, thrust, and lift of rotorcraft 101.
  • Rotorcraft 101 further includes a fuselage 107, anti-torque system 109, an empennage 111, and a tail structure 120.
  • tail structure 120 can represent a horizontal stabilizer.
  • FIGURE 1A also illustrates an engine cowling 119 for covering a rotorcraft and an engine inlet 117, which are located aft of the rotor linkages.
  • FIGURE 1A further illustrates a transmission cowling 115 for covering a rotorcraft transmission.
  • FIGURE 1B further illustrates an exemplary location of an exhaust manifold structure 121 disclosed herein, in accordance with various embodiments. As depicted, the exhaust manifold 121 is located forward of engine inlet 117.
  • cowl, cowling, and fairing may be used interchangeably.
  • rotorcraft 101 of FIGURES 1A and 1B are merely illustrative of a variety of aircraft that can be used to implement embodiments of the present disclosure.
  • Other aircraft implementations can include, for example, fixed wing airplanes, hybrid aircraft, unmanned aircraft, gyrocopters, and a variety of helicopter configurations, among other examples.
  • helicopter configurations among other examples.
  • aircraft are particularly well suited to implement embodiments of the present disclosure, the described embodiments can also be implemented using non-aircraft vehicles and devices.
  • the embodiments described throughout this disclosure provide numerous technical advantages, including providing full access to equipment for performing maintenance and service without having to remove the access door. Further, the bi-folding door enables a single maintenance worker to open and close the door while providing full access to the equipment.
  • Example embodiments that may be used to implement an exhaust manifold for combining and expelling multiple exhaust paths towards the rotor linkages, such that the exhaust dissipates upwards and away from the engine inlets, are described below with more particular reference to the remaining FIGURES.
  • FIGURE 2 illustrates an exhaust manifold for combining exhaust paths, in accordance with various embodiments.
  • exhaust manifold 200 includes a platform 202 having multiple openings or exhaust ducts on the top side 204, 206, 208, 210 and corresponding air ducts 214, 216, 218, 220 on the bottom side.
  • the exhaust may be pulled through the ducts using any suitable means, such as a squirrel cage fan, an impeller, and/or a blower.
  • exhaust from a transmission oil cooler may be pulled through air ducts 214, 216 and exhaust ducts 204, 206, then, expelled towards the rotor linkages.
  • the exhaust may be pushed through the ducts using any suitable means, such as, by an impeller on the system that is creating the exhaust.
  • air ducts 218, 220 may be connected to a plenum in a generator with flexible hosing and an impeller located in the generator may push the exhaust air from the generator through the exhaust ducts 208, 210.
  • Platform 202 may be any suitable size and shape to fit within a top region of the rotorcraft and to provide sufficient area for containing and connecting multiple exhaust paths and directing them towards the rotor disc. As shown in FIGURE 2 , the platform may be shaped as a half of an oval or a semi-circle. In some embodiments, platform 202 may have multiple planes such that the platform curves upwards or downwards, in accordance with the contours of the surface of the aircraft. In some embodiments, platform 202 may be a single platform. In some embodiments, platform 202 may multiple platforms that may be arranged in a stacked, staggered, side-by-side, or any other suitable configuration. Platform 202 may be made of any suitable material, including metallic, nonmetallic or a combination thereof, for example, fiberglass, steel, and aluminum, and may be made of the same material as the cowling.
  • platform 202 may include exhaust ducts 204, 206, 208, 210 and air ducts 214, 216, 218, 220 for directing exhaust paths from a system, or from multiple systems, and expelling the exhaust towards the rotor linkages.
  • Air ducts on the exhaust manifold may be attached directly or indirectly to the corresponding system by any suitable structure, such as rigid plumbing, flexible hoses, accordion style ducts, among others, or a combination thereof.
  • Air duct paths may be combined on the underside of platform 202 such that multiple air ducts flow into a single exhaust duct on the upper side of platform 202 (not shown).
  • air ducts 218, 220 may be combined to flow into a single exhaust duct (not shown).
  • An exhaust duct 204, 206, 208, 210 may be any suitable shape and size to effectively flow the system exhausts into the rotor linkages. Exhaust ducts may include features for directing exhaust in a direction, such as, towards the rotor discs rather than the rotors, which may be more affected by air temperature variations.
  • exhaust ducts 204, 206 are circular with a flange 205, 207 around the circumference that extends beyond the surface of platform 202 and angles towards the rotor disc.
  • the flange 205, 207 has a higher edge on the front side of the duct, which is away from the rotor disc and towards the front side of the aircraft 230, and a lower edge on the back side of the duct, which is towards the rotor disc and towards the back side of the aircraft 231, to direct the exhaust towards the rotor disc.
  • Exhaust ducts may include other features for directing flow, such as, contouring along the inner sides, tapering of the air duct and/or exhaust duct, among others, or a combination thereof.
  • Air ducts and exhaust ducts may be attached to platform 202 using any suitable means, including adhesive, glue, and a metal holder with screws, among others, or a combination thereof.
  • the interface between the duct and the platform may be sealed using any suitable sealing mechanisms, such as o-rings, adhesive, epoxy, and gaskets, among others, or a combination thereof, to prevent the exhaust from dissipating before flowing through the exhaust duct.
  • Exhaust manifold 200 may include mechanisms 222 for mechanically connecting platform 202 of the exhaust manifold to the rotorcraft, including attaching the platform to a cowl on the rotorcraft. These mechanisms may include, for example, screws, rivets, hasp clasps, compression latches, and draw latches, among others, or a combination thereof. Platform 202 may further include weather stripping or other material where the platform connects 222 to the rotorcraft for sealing and protecting against rust and other types of weather damage.
  • FIGURE 3 illustrates an exhaust manifold 300 for combining exhaust paths, in accordance with various embodiments.
  • FIGURE 3 is exhaust manifold 200 of FIGURE 2 with additional exhaust duct 302 and air duct 304 for expelling exhaust from an environmental control system (ECS), which may control air temperature and air quality in a rotorcraft cabin.
  • ECS environmental control system
  • air duct 304 may receive exhaust from an ECS. The exhaust may flow through air duct 304, and may be expelled through exhaust duct 302 towards the rotor linkages.
  • an exhaust manifold may include any number of air ducts and exhaust ducts, and may be configured to optimize the number and placement of ducts.
  • the size and shape of an air duct cross section is the same as the exhaust duct.
  • the size and shape of the cross sections of the air duct and exhaust duct are the same, whereas as shown for ducts 204, 214 and 206, 216, the size and shape of the cross sections of the air duct and exhaust duct are different (i.e., circular as compared to square).
  • the size and shape of the air duct and exhaust duct may be optimized, for example, based on the amount of exhaust received, the type of ducting used, and the method for moving the exhaust through the ducts.
  • FIGURE 4 illustrates an exhaust manifold 400 for combining exhaust paths having a cowl support structure 404, in accordance with various embodiments.
  • Cowl support structure 404 may be of any suitable size and shape to provide support to a cowl that overlays the structure.
  • cowl support structure 404 may be a frame that attaches to one or more sides and/or the underside 402 of the exhaust manifold platform 202.
  • Support structure 404 may be attached using any suitable means, such as screws, and snap fasteners, among others, or a combination thereof.
  • Support structure 404 may be legs that extend from the underside of platform that are shaped to follow the contour of the cowl, such that the cowl lays along the entire support structure.
  • the support structure may be shaped to follow a portion of the contour of the cowl, such that the support structure supports a portion of the cowl.
  • a support structure may be shaped to follow a top portion of a contour of a cowl where a cowl may lay along only the top portion of the support structure and the legs may extend straight down rather than curving to match the full contour of the cowl.
  • Cowl support structure 404 may be made of any suitable material, such as steel and hydroformed aluminum, among others, to provide support and stability to a cowl. Cowl support structure 404 may be attached to the floor of the equipment area where the exhaust manifold is located using any suitable means, such as screws and rivets, among others.
  • the cowl may not be attached to the support structure and may simply lay over the support structure. In some embodiments, the cowl may be attached to the support structure and may be attached using any suitable means, such as screws and rivets, among others, or a combination thereof.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Exhaust Silencers (AREA)

Claims (5)

  1. Giravion (101) comprenant :
    un moteur ;
    une entrée de moteur (117) ;
    une liaison de rotor ; et
    un collecteur d'échappement (200, 300, 400) comprenant :
    une pluralité de conduits d'échappement (204, 206, 208, 210, 302) en communication gazeuse avec un ou plusieurs systèmes d'échappement, dans lequel les conduits d'échappement (204, 206, 208, 210, 302) reçoivent des gaz d'échappement provenant des un ou plusieurs systèmes d'échappement ; et
    une plate-forme (202) comprenant la pluralité de conduits d'échappement (204, 206, 208, 210, 302), dans lequel la plate-forme (202) est située en amont de l'entrée de moteur, et dans lequel la pluralité de conduits d'échappement (204, 206, 208, 210, 302) sont configurés pour diriger les gaz d'échappement vers la liaison de rotor.
  2. Giravion (101) selon la revendication 1, dans lequel le un ou plusieurs systèmes d'échappement incluent un ou plusieurs parmi une transmission, un refroidissement d'huile, un générateur et un système de conditionnement d'air.
  3. Giravion (101) selon la revendication 1, comprenant en outre :
    un capot, dans lequel la plate-forme (202) est fixée au capot ; et
    une structure de support de capot (404), dans lequel la structure de support de capot (404) supporte le capot auquel la plate-forme (202) est fixée.
  4. Giravion (101) selon la revendication 3, dans lequel la structure de support de capot (404) correspond à un contour du capot.
  5. Giravion (101) selon la revendication 3, dans lequel la structure de support de capot (404) correspond à une partie d'un contour du capot.
EP17203232.8A 2017-09-22 2017-11-23 Giravion avec collecteur d'échappement permettant de combiner un panache d'échappement de système Active EP3459845B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19189876.6A EP3584160B1 (fr) 2017-09-22 2017-11-23 Collecteur d'échappement permettant de combiner des fumées d'échappement de système

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/713,207 US10480386B2 (en) 2017-09-22 2017-09-22 Exhaust manifold for combining system exhaust plume

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP19189876.6A Division EP3584160B1 (fr) 2017-09-22 2017-11-23 Collecteur d'échappement permettant de combiner des fumées d'échappement de système
EP19189876.6A Division-Into EP3584160B1 (fr) 2017-09-22 2017-11-23 Collecteur d'échappement permettant de combiner des fumées d'échappement de système

Publications (2)

Publication Number Publication Date
EP3459845A1 EP3459845A1 (fr) 2019-03-27
EP3459845B1 true EP3459845B1 (fr) 2019-09-18

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ID=60450556

Family Applications (2)

Application Number Title Priority Date Filing Date
EP19189876.6A Active EP3584160B1 (fr) 2017-09-22 2017-11-23 Collecteur d'échappement permettant de combiner des fumées d'échappement de système
EP17203232.8A Active EP3459845B1 (fr) 2017-09-22 2017-11-23 Giravion avec collecteur d'échappement permettant de combiner un panache d'échappement de système

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Application Number Title Priority Date Filing Date
EP19189876.6A Active EP3584160B1 (fr) 2017-09-22 2017-11-23 Collecteur d'échappement permettant de combiner des fumées d'échappement de système

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US (1) US10480386B2 (fr)
EP (2) EP3584160B1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112160804B (zh) * 2020-09-25 2023-03-24 中国直升机设计研究所 一种发动机排气管整流罩
FR3149592B1 (fr) 2023-06-09 2025-05-02 Airbus Helicopters Aéronef muni d’un système de ventilation anti-pluie pour une machine électrique

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Publication number Priority date Publication date Assignee Title
US2119402A (en) * 1935-06-26 1938-05-31 Gen Electric Aircraft
US2503172A (en) * 1942-08-17 1950-04-04 Cierva Autogiro Co Ltd Helicopter with jet reaction for counteracting torque
GB638093A (en) 1947-08-18 1950-05-31 Rotol Ltd Improvements in or relating to aircraft gas-turbine-engine power plants
US3792827A (en) * 1972-11-10 1974-02-19 Teledyne Ryan Aeronautical Inc Vtol aircraft with cruciform rotor wing
US4071009A (en) * 1976-06-28 1978-01-31 Caterpillar Tractor Co. Combined noise suppressing and air flow guide enclosure for engines
US4216924A (en) 1978-12-20 1980-08-12 United Technologies Corporation Helicopter
US5052176A (en) * 1988-09-28 1991-10-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Combination turbojet-ramjet-rocket propulsion system
US7147182B1 (en) * 2004-02-23 2006-12-12 Kenneth Warren Flanigan Gas-powered tip-jet-driven tilt-rotor compound VTOL aircraft
US7823375B2 (en) * 2005-08-01 2010-11-02 Sikorsky Aircraft Corporation Infrared suppression system
US7600711B1 (en) * 2006-05-16 2009-10-13 The Boeing Company Flexible ducting system including an articulable sealed joint
US20140060004A1 (en) 2011-09-20 2014-03-06 Bell Helicopter Textron Inc. Tiltrotor vectored exhaust system
EP2719620A3 (fr) 2012-10-10 2017-10-18 Sikorsky Aircraft Corporation Système d'échappement tourné vers le haut pour aéronef à voilure tournante
EP2724934B1 (fr) 2012-10-26 2016-09-21 AGUSTAWESTLAND S.p.A. Aéronef capable d'effectuer du vol stationnaire
US10415475B2 (en) 2014-07-31 2019-09-17 Sikorsky Aircraft Corporation Gearbox oil cooling assembly

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Title
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Also Published As

Publication number Publication date
EP3584160B1 (fr) 2022-08-31
EP3459845A1 (fr) 2019-03-27
US10480386B2 (en) 2019-11-19
US20190093541A1 (en) 2019-03-28
EP3584160A1 (fr) 2019-12-25

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